ASTM F3479-20

Standard Specification for Failure Tolerance for Occupant Safety of Suborbital Vehicles

SCOPE
1.1 This specification provides system safety engineering and failure tolerance requirements applicable to occupant safety for suborbital vehicles.  
1.2 This specification is not intended to provide failure tolerance requirements for conditions that do not impact occupant safety. For example, conditions resulting in facility damage, vehicle damage, loss of mission objectives, or adverse impact to public safety that do not also have an impact to occupant safety are not subject to the requirements identified in this specification. This specification does not address malfunctions caused by malicious attacks on software systems.  
1.3 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.4 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

General Information

• Status: Published
• Publication Date: 30-Sep-2020
• ICS: 49.020 - Aircraft and space vehicles in general
• ICS: 49.140 - Space systems and operations
• Technical Committee: F47 - Commercial Spaceflight
• Drafting Committee: F47.01 - Occupant Safety

Standards Content (Sample)

This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the
Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
Designation:F3479 −20
Standard Specification for
Failure Tolerance for Occupant Safety of Suborbital
1
Vehicles
This standard is issued under the fixed designation F3479; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
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1. Scope 2.2 RTCA Standards:
RTCA DO-178 Software Considerations in Airborne Sys-
1.1 This specification provides system safety engineering
tems and Equipment Certification
and failure tolerance requirements applicable to occupant
RTCADO-278 Software IntegrityAssurance Considerations
safety for suborbital vehicles.
for Communication, Navigation, Surveillance and Air
1.2 This specification is not intended to provide failure Traffic Management (CNS/ATM) Systems
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tolerance requirements for conditions that do not impact 2.3 SAE Standards:
SAE ARP 4754A Guidelines for Development of Civil
occupant safety. For example, conditions resulting in facility
Aircraft and Systems
damage, vehicle damage, loss of mission objectives, or adverse
SAEARP 4761 Guidelines and Methods for Conducting the
impact to public safety that do not also have an impact to
SafetyAssessment Process on CivilAirborne Systems and
occupantsafetyarenotsubjecttotherequirementsidentifiedin
Equipment
this specification. This specification does not address malfunc-
2.4 Other Standards:
tions caused by malicious attacks on software systems.
IEEE/EIA 12207 International Standard - Systems and soft-
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1.3 This standard does not purport to address all of the
ware engineering
safety concerns, if any, associated with its use. It is the
MIL-STD-882E Department of Defense Standard Practice
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responsibility of the user of this standard to establish appro-
System Safety
priate safety, health, and environmental practices and deter-
3. Terminology
mine the applicability of regulatory limitations prior to use.
1.4 This international standard was developed in accor-
3.1 Definitions:
dance with internationally recognized principles on standard- 3.1.1 catastrophic event—loss of life or permanent disabil-
ity for the purposes of this specification.
ization established in the Decision on Principles for the
Development of International Standards, Guides and Recom-
3.1.2 failure condition—a condition, or set of conditions,
mendations issued by the World Trade Organization Technical
that affects the operation of a component, part, or element such
Barriers to Trade (TBT) Committee.
that it can no longer function as intended. Types of failure
conditions that should be considered include:
2. Referenced Documents
3.1.2.1 incorrect function—incorrect functional output(s),
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when required, and functional outputs produced at the wrong
2.1 NASA Handbooks:
time (inadvertent function).
NASA/SP-2010-580 NASA System Safety Handbook Vol-
ume 1: System Safety Framework and Concepts for
3.1.2.2 loss of function—theabsenceoffunctionaloutput(s),
Implementation
when required.
NASA/SP-2014-612 NASA System Safety Handbook Vol-
3.1.2.3 safety critical function or item—a failure of the
ume 2: System Safety Concepts, Guidelines, and Imple-
function or item causes one or more failure conditions that
mentation Examples
result in a catastrophic event.
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Available from RTCA, Inc. (RTCA), 1150 18th NW, Suite 910, Washington,
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This specification is under the jurisdiction of ASTM Committee F47 on DC 20036, https://www.rtca.org.
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Commercial Spaceflight and is the direct responsibility of Subcommittee F47.01 on Available from SAE International (SAE), 400 Commonwealth Dr.,Warrendale,
Occupant Safety of Suborbital Vehicles. PA 15096, http://www.sae.org.
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Current edition approved Oct. 1, 2020. Published November 2020. DOI: Available from Institute of Electrical and Electronics Engineers, Inc. (IEEE),
10.1520/F3479-20 445 Hoes Ln., Piscataway, NJ 08854-4141, http://www.ieee.org.
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Available from NASATechnical Reports Server (NTRS), NASAHeadquarters, Available from DLA Document Services, Building 4/D, 700 Robbins Ave.,
300 E. Street, SW, Suite 5R30, Washington, DC 20546, https://ntrs.nasa.gov. Philadelphia, PA 19111-5094, http://quicksearch.dla.mil.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
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F3479−20
3.1.3 failure tolerance—the ability to sustain a certain (1) Software development methods and standards, includ-
number of failures and still retain capability to satisfy safety ing how intended software be
...